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A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial sectio

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; an outer cowl connected to the dome plate outer portion at a downstream end thereof; an inner cowl connected to the dome plate inner portion at a downstream end thereof; and, a deflector plate connected to and positioned aft of each opening in the dome plate. Each deflector plate further includes: an annular section at an upstream end thereof having a forward end, an aft end, an inner surface and an outer surface; a substantially planar flange connected to the aft end of the annular section, the planar flange including an outer circumferential surface, an inner circumferential surface, a first radial surface, a second radial surface, and an opening therein sized to the inner surface of the annular section so as to form opposing radial sections; a first flange connected to the outer circumferential surface of the planar flange at a predetermined angle thereto; and, a second flange connected to the inner circumferential surface of the planar flange at a predetermined angle thereto. The first and second radial sections of the deflector plate planar flange are configured so at least a portion of the dome plate cooling trough is in flow communication with a combustion chamber downstream of said dome plate.

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What is claimed is: 1. A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed the

What is claimed is: 1. A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of said openings includes a cooling trough formed therein; and, (b) an outer cowl connected to said dome plate outer portion at a downstream end thereof; (c) an inner cowl connected to said dome plate inner portion at a downstream end thereof; and, (d) a deflector plate connected to and positioned aft of each said opening in said dome plate, each deflector plate further comprising: (1) an annular section at an upstream end thereof having a forward end, an aft end, an inner surface and an outer surface; (2) a substantially planar flange connected to said aft end of said annular section, said planar flange including an outer circumferential surface, an inner circumferential surface, a first radial surface, a second radial surface, and an opening therein sized to said inner surface of said annular section so as to form opposing first and second radial sections; (3) a first flange connected to said outer circumferential surface of said planar flange at a predetermined angle thereto; and, (4) a second flange connected to said inner cicumuferential surface of said planar flange at a predetermined angle thereto; wherein said first and second radial sections of said deflector plate planar flange are configured so at least a portion of each said dome plate cooling trough is in flow communication with a combustion chamber aft of said dome plate. 2. The combustor dome assembly of claim 1, each cooling trough of said dome plate including at least one purge opening formed in a middle portion thereof which is substantially larger in diameter than a plurality of cooling holes fanned in said cooling trough. 3. The combustor dome assembly of claim 2, wherein a collective sits of said purge openings is equivalent to a predetermined amount. 4. The combustor dome assembly of claim 1, wherein said first and second radial sections of said deflector plate planar flange have a notched portion farmed therein so as to reduce stress imposed thereon. 5. The combustor dome assembly of claim 4, wherein said notched portions in said first and second radial sections are located at a point having a minimum circumferential length. 6. The combustor dome assembly of claim 4, wherein said notched portions in said first and second radial sections are substantially arcuate. 7. The combustor dome assembly of claim 4, wherein said notched portions in said first and second radial sections have a predetermined radial length. 8. The combustor dome assembly of claim 4, wherein said notched portions in said first and second radial sections have a predetermined circumferential length. 9. The combustor dome assembly of claim 4, wherein said first and second radial sections maintain a minimum circumferential length as said notched portions. 10. The deflector plate of claim 4, wherein radial surfaces of said planar flange are configured where said notched portions in said first and second radial sections are nonlinear. 11. The deflector plate of claim 10, wherein said notched portions in said first and second radial sections include a chamfer. 12. The deflector plate of claim 11, wherein said chamfer is formed in conjunction with said aft surface of said planar flange. 13. A deflector plate for a gas turbine engine combustor having a longitudinal centerline axis therethrough, comprising: (a) an annular section at an upstream end thereof having a forward end, an aft end, an inner surface and an outer surface; (b) a substantially planar flange connected to said aft end of said annular section, said planar flange including an outer circumferential surface, an inner circumferential surface, a flit radial surface, a second radial surface, and an opening therein sized to said inner surface of said annular section so as to form opposing first and second radial sections; (c) a first flange connected to said outer circumferential surface of said planar flange at a predetermined angle thereto; and, (d) a second flange connected to said inner circumferential surface of said planar flange at a predetermined angle thereto; wherein said first and second radial sections include a notched portion so as to reduce stress imposed on said radial sections of said planar flange. 14. The deflector plate of claim 13, wherein said notched portions in said first and second radial sections are located at a point having a minimum circumferential length. 15. The deflector plate of claim 13, wherein said notched portions in said first and second radial sections are substantially arcuate. 16. The deflector plate of claim 13, wherein said notched portions in said first and second radial sections have a predetermined radial length. 17. The deflector plate of claim 13, wherein said notched portions in said first and second radial sections have a predetermined circumferential length. 18. The deflector plate of claim 13, wherein said first and second radial sections maintain a minimum circumferential length at said notched portions. 19. The deflector plate of claim 13, wherein radial surfaces of said planar flange are configured where said notched portions in said first and second radial sections are nonlinear. 20. The deflector plate of claim 19, wherein said notched portions in said first and second radial sections include a chamfer. 21. The deflector plate of claim 20, wherein said chamfer is formed in conjunction with said aft surface of said planar flange. 22. The deflector plate of claim 13, wherein a thermal barrier coating is applied to an aft surface of said outer and inner radial flanges. 23. An annular dome plate for a gas turbine engine combustor having a longitudinal centerline axis therethrough, comprising: (a) an inner portion; (b) an outer portion; and, (c) a middle portion located between said inner and outer portions, wherein a plurality of circumferentially spaced openings are formed in said middle portion, said middle portion further comprising: (1) a radial section defined between each of said openings; and (2) a cooling trough formed in each radial section having a plurality of cooling holes formed therein and at least one purge opening of substantially greater size than said cooling holes formed therein. 24. The dome plate of claim 23, wherein each opening in said dome plate has at least a predetermined diameter. 25. The dome plate of claim 23, wherein a circumferential distance between adjacent openings in said dome plate is no greater than a predetermined amount. 26. The dome plate of claim 23, wherein said purge openings are formed in a middle portion of said cooling trough. 27. The dome plate of claim 23, wherein said purge openings are substantially circular. 28. The dome plate of claim 23, wherein said purge openings are substantially ovular. 29. The dome plate of claim 23, wherein said purge openings have a predetermined collective area.